US4238927A - Rotary exchanger for gas turbine installations - Google Patents

Rotary exchanger for gas turbine installations Download PDF

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Publication number
US4238927A
US4238927A US05/965,342 US96534278A US4238927A US 4238927 A US4238927 A US 4238927A US 96534278 A US96534278 A US 96534278A US 4238927 A US4238927 A US 4238927A
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United States
Prior art keywords
exchanger
matrices
accordance
exchange
roller
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Expired - Lifetime
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US05/965,342
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English (en)
Inventor
Raymond J. M. Joubert
Jean G. Bouiller
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Safran Aircraft Engines SAS
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Safran Aircraft Engines SAS
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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/08—Heating air supply before combustion, e.g. by exhaust gases
    • F02C7/10—Heating air supply before combustion, e.g. by exhaust gases by means of regenerative heat-exchangers
    • F02C7/105—Heating air supply before combustion, e.g. by exhaust gases by means of regenerative heat-exchangers of the rotary type
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F28—HEAT EXCHANGE IN GENERAL
    • F28D—HEAT-EXCHANGE APPARATUS, NOT PROVIDED FOR IN ANOTHER SUBCLASS, IN WHICH THE HEAT-EXCHANGE MEDIA DO NOT COME INTO DIRECT CONTACT
    • F28D19/00—Regenerative heat-exchange apparatus in which the intermediate heat-transfer medium or body is moved successively into contact with each heat-exchange medium
    • F28D19/04—Regenerative heat-exchange apparatus in which the intermediate heat-transfer medium or body is moved successively into contact with each heat-exchange medium using rigid bodies, e.g. mounted on a movable carrier
    • F28D19/045—Regenerative heat-exchange apparatus in which the intermediate heat-transfer medium or body is moved successively into contact with each heat-exchange medium using rigid bodies, e.g. mounted on a movable carrier with radial flow through the intermediate heat-transfer medium
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Definitions

  • This invention is in the field of rotary exchangers for gas turbine installations, in particular a modular exchanger entity and its sealing devices.
  • French Pat. No. 1,496,850 provides a solution for the use of exchangers for the recovery of heat from the combustion gases in an aircraft turbine.
  • the hot combustion gases and the compressed cold air coming from the compressor are simultaneously passed through the same heat exchanger paths.
  • Inside of the exchanger tubes in a first step, the heat of the hot gases is absorbed and then, in a second step, it is given off to the colder compressed air coming from the compressor and feeding the combustion chamber.
  • a distribution system of the hot gases and of the cold air is disposed in front of the ends of the exchanger tubes, carried by a rotary drum. By means of rotation, the tubes are successively located in front of each of the distributors and thus permit their successive sweeping by the hot gases and by the hot air.
  • the temperature of the exhaust gases extends through a temperature range of 550° to 850°, the rotating elements are subjected to significant temperature variations, which have the effect of a change in their geometrical dimension.
  • the patent which is mentioned below, succeeds in limiting this variation by circulating the cold air in the support components of the stationary parts and of the rotating parts of the exchanger. These supports form a part of the compressed air feed piping.
  • the exchanger matrices are comprised of tubes which are maintained between two annular supports. The exchanger tubes are fixed to only one of their ends, the other end being freely slidable in the support.
  • the gases are piped through the entire length of the exchanger tubes by resilient elements, which are fixed at their ends to the end supports of the rotor and which can move freely.
  • each end of the rotor has sealing means comprised of joint plates, which are radially disposed and extend over one portion of the upper circumference to the circumferential portion occupied by the collector taking or recovering the fluid going through the heat exchanger matrices.
  • the rotor has fixed inside and outside annular joints (with respect to the crown of the exchangers), which cooperate with similar joints on the fixed portion. These joints are formed of annular segments, which are resiliently urged in the axial direction and towards the rotor joint by springs.
  • the sealing device prevents radial losses.
  • the exchangers and their sealing devices in accordance with the present invention have the same objectives as the embodiments described above.
  • the invention furthermore proposes to provide a light weight and small dimension exchanger, these characteristics being due to a novel sealing system between the air and gas flows, as well as special features of the exchange matrices.
  • this rotary exchanger for gas turbine installations comprises thermal exchange matrices, disposed in accordance with at least one cylindrical ring, which turns about the axis of the turbine, means for the retention in rotation of the annular ring between two fixed housings, passages for the gaseous fluid between the housings and the exchange matrices, fixed rings, which close the ends of the housings and between which the cylindrical ring turns, means for the distribution of the fluids, a circumferential sealing device interposed between the said fixed rings and the ends of the cylindrical ring, an axial sealing device, which separates the passage of the hot and cold fluids between two cylindrical segments of the exchange matrices, is characterized in that the thermal exchange matrix is comprised of a thermal exchange material, which is included between the lateral inside and outside surfaces of the said cylindrical ring.
  • FIG. 1 is a longitudinal sectional view of a gas turbine, equipped with an exchanger in accordance with the invention
  • FIG. 2 is a sectional and perspective diagram of a rotary exchanger
  • FIG. 3 is a schematic sectional view taken on line III--III of FIG. 1;
  • FIG. 4 is a schematic sectional view taken on line IV--IV of FIG. 1;
  • FIG. 5 is a schematic sectional view taken on line V--V of FIG. 1;
  • FIG. 6 is a view taken on line III--III of FIG. 1, showing the mounting of the sections of FIGS. 3, 4 and 5;
  • FIG. 7 is a partly cut away view, in perspective, of the fluid distribution housing
  • FIG. 8 is a partial perspective view of the sealing joint, which connects the distribution housing to the conduit for the combustion gases;
  • FIG. 9 is a sectional view of a part of the exchanger.
  • FIG. 10 is a transverse section of a portion of the exchanger, showing the axial sealing means
  • FIG. 11 is a large scale view of the sealing means shown on the right side of FIG. 10.
  • FIG. 12 is a schematic view of the retention means of the exchange matrices and the sealing means.
  • FIG. 1 represents a schematic section of an aircraft gas turbine, which is equipped with a rotating exchanger.
  • the air admitted at the front passes into the compressor 1, where it is compressed before being conducted into the combustion chamber 2.
  • the compressed air/fuel mixture is ignited and the high speed combustion gases exhaust through turbine vanes 3, causing turbine rotation.
  • the gases of combustion are then evacuated through the jet pipe 4.
  • FIG. 2 schematically shows part A, in which the gases of combustion leave their heat and part B, in which the compressed air is heated. This part B represents a small portion with respect to the totality of the cylindrical exchanger.
  • Fluid distribution means 7, which will be detailed later, direct the distribution of the fluids in the two parts.
  • the exchange matrices 6 are disposed in cylindrical rings (FIG. 4) and turn concentrically with respect to each other and with respect to the axis of the turbine.
  • the cylindrical rings form the exchange matrices and are composed at least in part of a thermal exchange material, which is disposed between the inside and outside surfaces of the ring.
  • the material, which comprises the matrix is a material, which is coherent at considerable thermal inertia. It presents a permeability for the gases in the radial direction and, preferably, zero permeability in the circumferential direction.
  • a honeycomb material which is enclosed in sheetmetal, welded by electronic bombardment, would be suitable.
  • the cylindrical rings turn between two tight housings 8 and 9, which delimit, with the inside and outside surfaces of the cylindrical matrices, fluid passages 10 and 11.
  • a passage 12 also separates the exchange matrices from each other.
  • Fixed rings 39 and 40 which define the front and rear ends of the exchanger, receive distribution means for the fluids.
  • Circumferential sealing devices disposed between said rings and the ends of the exchange matrices, assure the passage of the gases from the fixed portion of the exchanger to the rotating matrices.
  • the axial tightness between the sectors receiving the hot gases and the compressed cold air is assured by an axial sealing device.
  • the gases of combustion (broad arrows) are directed through the intermediate conduit 13 (FIGS. 1 and 3) and of distribution ring 14 (FIG. 4) into space 12, which is located between matrices 6, corresponding to sector A of FIG. 2.
  • the hot gases go through the exchange material, which comprises matrices 6 (double arrows) (FIG. 5), where they lose their heat and are evacuated through jet pipe 4.
  • FIG. 5 schematically shows delimiting passage 10 for the compressed cold air between means 20, housing 8 and matrix 6, passage 12 through which the heated compressed air passes again between means 21 and adjacent matrices 6 and passage 11 for the compressed cold air between means 22, matrix 6 and housing 9.
  • FIG. 6, which is obtained by the superposition of the sections represented by FIGS. 3, 4 and 5, shows the disposition of the distribution means with respect to the rear end of the exchanger.
  • FIG. 7 is a partly cut away perspective view of the said distribution means.
  • Conduits 15 open into a distribution box 16, from which two semi annular pipes 17 exit.
  • Conduit 13 ends in a semi annular distributor 14.
  • a housing 19 heads the rear part of the exchanger and also covers the semi annular distributor 14, which are disposed, for their greatest part, inside housing 19.
  • the exchanger which is the object of this invention, it presents itself in the form of a modular assembly.
  • the exchanger and the fluid distributors form an entity, which is easily disassembled from the body of the reactor.
  • the rear end of the exchanger is headed by a distribution housing 19, which includes the connecting conduits, which are easily accessible and connectible to the conduits coming from the compressor or going to the combustion chamber through sliding sleeves 25, which are in themselves known.
  • the connection of the outlet ring of the turbine to conduit 13 for the recovery of heat from the hot combustion gases presents a peculiarity, which assures a good tightness, while offering a maximum passage for the high temperature gases.
  • the annular-shaped conduit 13 (FIG.
  • FIG. 7 The partially cut away view of FIG. 7 shows this arrangement.
  • the flanges are made from two elastic bands, which are profiled in the form of a J (FIG. 8). Each band has notches 29, which radially cut a part of the profile. Two of these bands are arranged on top of each other and are welded together and to the edge of the piping in such a way that the notches on one correspond to the plain segments of the other.
  • This arrangement results in the assurance of tightness, while maintaining the elasticity of curved part 30 of the profile.
  • This elastic flange cooperates with a U-shaped inverse profile, which is attached to the end of the outlet ring of the turbine.
  • Flange 28 is resiliently held against the lateral branches of the U profile 31, maintaining an accurate centering of pipings 13 and 32, while permitting expansion and assuring tightness.
  • a similar inversely arranged U profile assures tightness with flange 27.
  • the housing is pear-shaped and is truncated at the lower end, parallel and perpendicular to its axis. It goes without saying that other simpler embodiments are also suitable, for example, a parallel base truncated cone, a spherical zone or other volume capable of heading the end of the exchanger.
  • FIG. 9 shows a partial sectional view of an exchanger in accordance with the invention.
  • the fluid distribution housing 19 is attached to housing 8 of the exchanger.
  • the ends of the exchange matrices form an annular chamber, which is open to the outside in the axial direction.
  • Edges 36 of the chamber are machined in such a manner as to form a lip with a reduced surface, being supported on the cylindrical segment 37, of a heat-resistant material, having a reduced coefficient of friction and assuring a good tightness.
  • the material which is used is graphite.
  • Supports 38 are formed by front and rear fixed rings 39 and 40, on the faces of which annular chambers 41 are provided.
  • the space included between rings 42 and the lateral walls of the annular chambers 41 receives cylindrical segments 37, which assure the tightness.
  • Elastic means 45 press the annular segments 37 against the edges of the exchange matrices.
  • Elastic means 45 are comprised of a corrugated spring steel washer, of which at least one crown of the corrugation is supported against the back of a cylindrical segment.
  • the cylindrical segments are pseudo-cylinders, which are deformable axially, allowing the absorption of dimensional variations due to production tolerances and due to heat expansion, while still assuring a constant axial seal of the ends of the exchange matrices.
  • the edges of an exchange matrix thus cooperate with a deformable double cylinder of frictional material, comprised of the cylindrical segments.
  • the rotation and the centering of the cylindrical exchange matrices is obtained through frictional rollers 46 and 47, which are disposed at the ends of the matrices.
  • the frictional rollers are distributed uniformly over the circumference in such a manner as to alternate one frictional roller 46, which assures radial centering, and one frictional roller 47, which assured axial centering.
  • These frictional rollers are maintained in a frame, which is attached to the U-section ring 42.
  • a raceway 48 which cooperates with the axial centering frictional rollers 47, is preferably provided at the base of circular chamber 35. Radially centering frictional rollers 46 cooperate with a lateral inside wall of chamber 35.
  • the rear end of the exchangers, and more particularly the fixed ring 40 has, as ring 39, annular chambers, in which U-profile rings are placed.
  • the rings hold frames for restraining the centering frictional rollers and a stage 50, which cooperates with an arbor 51, which is equipped, at one of its ends, with a gear-wheel 52, which is kept in rotation by a gear train, which will be described below.
  • the other end of arbor 51 has a gearwheel 54 and a friction roller 55. This train cooperates with a rack 56, cut or supported on one wall of annular chamber 35, which is provided at the rear end of the exchange matrix.
  • the frictional roller 55 which is in one piece with axis 51 and gearwheel 54, cooperates with a roller train 53, which is provided on the lateral wall, which also carries rack 56.
  • Each exchange matrix comprises an identical drive assembly.
  • the matrix assemblies cooperate with each other and with a transmission pinion in accordance with an arrangement, which will be described below.
  • the axial sealing between the exchange matrices which allow a separation of parts A and B, which receive the hot combustion gases and the compressed cold air, is obtained by two assemblies, including rollers 57 and 58, arranged between two adjacent exchange matrices 61 and 62 (FIG. 10) and two rollers 59 and 60, which are located on the outer and inner sides of the matrices.
  • Roller 59 assures tightness between the outside surface of matrix 61 and the outside housing 8, through a sealing device, which will be described below, and roller 60 between the inside surface of matrix 62 and inside housing 9 through a device similar to the above.
  • rollers which assure tightness between matrices 61 and 62.
  • the same sealing device can be designed with only one roller, tangent, with two of its radii, to the walls of the matrix, or with three or more rollers.
  • An example with three rollers is illustrated in FIG. 5.
  • the exchange matrices must rotate in opposite directions or in the same direction.
  • the rollers are comprised, for example, of a rigid tube 63, which is covered by a relatively flexible material 64.
  • the ends of the tube are provided with hollow cylindrical parts 65 with axles 66.
  • the rollers are arranged in such a manner as to be tangent to one of the radii of the exchange matrices.
  • the rollers, which are located in space 12 between matrices are tangent to these matrices and to each other. At their ends, they are held by pillow-blocks, which are in themselves known and not shown and which cooperate with their axles.
  • rollers 57 and 58 serve only to support the roller in rotation
  • the rear axles, extending through ring 40 are equipped with gearwheels 67, which permit their rotational drive in accordance with a process, which will be described below.
  • gearwheels 67 which permit their rotational drive in accordance with a process, which will be described below.
  • roller 57 is provided with pillow-blocks, which allow only a radial displacement
  • roller 58 is provided with pillow-blocks, allowing a displacement in the radial and circular directions. It is, of course, understood that another motional function is possible between rollers 57 and 58.
  • Rollers 59 and 60 need only a radial movement.
  • the rollers exert a permanent pressure on the radii of the exchange matrices, which assures a longitudinal seal between the arcuate spaces located around the rollers.
  • the pressure is exerted through pressure means acting on the pillow-blocks, which cooperate with the axles of the rollers.
  • the longitudinal and circumferential seal between sectors A and B (FIG. 11) for spaces 10 and 11, which are located between housings 8 and 9 and the exchange matrices 6, is realized by an elastic bearing and sealing device for the rollers, which is comprised of a fixed groove 71, parallel to the roller, at its base or fixed housing 8 or 9.
  • a flexible metal band 72 attached at one end to edge 73 of the groove, surrounds the roller over part of its circumference and is supported by a second round edge 74 of the groove.
  • the other end of band 72 is attached to an elastic traction device, comprised, in accordance with the embodiment, by springs 75 applying a tractional force directly or through the intermediate of cables 76 and pulleys 77.
  • band 72 which assures frictional tightness on the part of the roller and by support on the rounded edge of the groove, is comprised of several bands, which are arranged side by side without spaces therebetween.
  • FIG. 10 shows an embodiment in which the elastic traction device is common to two of the roller sealing devices, assuring tightness between sectors A and B.
  • the rotational drive of the exchange matrices and of the rollers is obtained through pinions, of which the synchronization is assured by gear trains.
  • the drive means corresponding to the example of FIG. 9 comprise two exchange matrices and two sealing rollers between the matrices and are shown at the rear of the exchanger, FIG. 12.
  • the sealing means has been illustrated as being disposed on one side between exchange sectors A and B and the illustration of various gear trains has been foreshortened to one plane.
  • the same references have been used as in FIG. 10.
  • the exchange matrices are driven in rotation by a separate motor, a turbine or a power take-off on the turbine (not shown) through a pinion 80.
  • This pinion engages pinions 79 and 52 at the ends of the arbors, of which the other ends have pinions 78 and 54, which cooperate with racks 56.
  • the drive train which is so constructed, makes the rotation of the exchange matrices in the same direction possible.
  • the drive of the rollers is accomplished through the intermediate of racks 56 of the exchange matrices.
  • a pinion 82 which, in accordance with the embodiment shown, is independent of the gear train driving the matrices, engages with rack 56 and transmits the motion to roller 57 through gear train 83.
  • a pinion 84 which cooperates with the solid pinion 86 of roller 59, is fixed on this gear train.
  • Roller 58 is driven in rotation by the surfaces of roller 57 and the periphery of exchange matrix 6.
  • roller 60 is driven through pinion 85, which engages with rack 56 of the exchange matrix.
  • the ratios of the diameters of the pinions are calculated in such a manner that the linear speeds of the surface of the driven rollers and of the exchange matrices are compatible with each other.
  • the rollers can be directly rotationally driven by the gear train, which drives the exchange matrices.
  • the drive means disposed at the rear of the exchanger are enclosed in a housing, which is not shown.
  • this housing is equipped with conduits for the cooled exhaust gases, combining to form jet pipe 4.
  • Rotary exchangers produced in accordance with the same characteristics as those described in the above examples, may have a single ring or exchange matrix.
  • the axial sealing devices are then reduced to two roller assemblies, such as those illustrated as 59 and 60 in FIG. 10.
  • exchangers can also comprise three or more coaxial rings or matrices.
  • the axial sealing devices would then be installed between the two roller assembly exchange matrices, such as illustrated as 57 and 58 in FIG. 10, or with three rollers as shown at 21 in FIG. 5, or even by alternating devices with two and three rollers.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Physics & Mathematics (AREA)
  • Thermal Sciences (AREA)
  • Heat-Exchange Devices With Radiators And Conduit Assemblies (AREA)
US05/965,342 1977-12-05 1978-12-01 Rotary exchanger for gas turbine installations Expired - Lifetime US4238927A (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR7737108A FR2413552A1 (fr) 1977-12-05 1977-12-05 Echangeur rotatif pour installations a turbine a gaz
FR7737108 1977-12-05

Publications (1)

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US4238927A true US4238927A (en) 1980-12-16

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US05/965,342 Expired - Lifetime US4238927A (en) 1977-12-05 1978-12-01 Rotary exchanger for gas turbine installations

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US (1) US4238927A (enExample)
DE (1) DE2852561A1 (enExample)
FR (1) FR2413552A1 (enExample)
GB (1) GB2009908B (enExample)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US12416263B2 (en) 2023-05-01 2025-09-16 General Electric Company Rotatable heat exchanger for a gas turbine engine

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2769081B1 (fr) * 1997-09-26 2000-05-19 Victor Sorokine Les appareils thermodynamiques avec recuperateur

Citations (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB683282A (en) 1943-01-28 1952-11-26 Gyorgy Jendrassik Improvements in or relating to heat exchangers
FR1147837A (fr) 1955-04-21 1957-11-29 B M W Studiengesellschaft Fuer Régénérateur à échange thermique
US3145534A (en) * 1960-01-20 1964-08-25 Williams Res Corp Heat exchanger for gas turbines
US3162241A (en) * 1961-10-25 1964-12-22 Continental Aviat & Eng Corp Seal for rotary regenerator
US3177928A (en) * 1962-04-26 1965-04-13 United Aircraft Corp Regenerative heat exchanger
DE1221850B (de) * 1959-05-15 1966-07-28 Daimler Benz Ag Gasturbinentriebwerk
US3294156A (en) * 1965-01-21 1966-12-27 Caterpillar Tractor Co Rotary regenerator
FR1517690A (fr) 1966-01-07 1968-03-22 Productions Ind Et De Distrib échangeur de chaleur rotatif ou analogue et ses diverses applications
US3389746A (en) * 1967-06-21 1968-06-25 Avco Corp Rotary regenerator having concentric cylindrical matrices

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US2892615A (en) * 1953-06-12 1959-06-30 Carrier Corp Heat exchangers of the rotary regenerator type
US2970815A (en) * 1953-09-10 1961-02-07 Linderoth Erik Torvald Regenerative heat exchanger for gas turbines
CH373921A (de) * 1958-09-10 1963-12-15 Gen Motors Corp Gasturbinentriebwerk
US3216487A (en) * 1962-09-04 1965-11-09 Solar Aircraft Co Regenerators
FR1442368A (fr) * 1965-04-15 1966-06-17 Gen Motors Corp Moteur à turbines à gaz comportant un récupérateur de chaleur rotatif
US3360275A (en) * 1966-01-25 1967-12-26 Gen Motors Corp By-pass seal
GB1153672A (en) * 1966-09-13 1969-05-29 George Garnham Turner Rotary Thermal Regenerator
GB1452290A (en) * 1973-10-24 1976-10-13 Advanced Materials Eng Rotor for rotary regenerative heat exchanger
US3848663A (en) * 1973-11-19 1974-11-19 Ford Motor Co Rotary regenerator for a gas turbine engine with resilient mounts for positioning the regenerator

Patent Citations (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB683282A (en) 1943-01-28 1952-11-26 Gyorgy Jendrassik Improvements in or relating to heat exchangers
FR1147837A (fr) 1955-04-21 1957-11-29 B M W Studiengesellschaft Fuer Régénérateur à échange thermique
DE1221850B (de) * 1959-05-15 1966-07-28 Daimler Benz Ag Gasturbinentriebwerk
US3145534A (en) * 1960-01-20 1964-08-25 Williams Res Corp Heat exchanger for gas turbines
US3162241A (en) * 1961-10-25 1964-12-22 Continental Aviat & Eng Corp Seal for rotary regenerator
US3177928A (en) * 1962-04-26 1965-04-13 United Aircraft Corp Regenerative heat exchanger
US3294156A (en) * 1965-01-21 1966-12-27 Caterpillar Tractor Co Rotary regenerator
FR1517690A (fr) 1966-01-07 1968-03-22 Productions Ind Et De Distrib échangeur de chaleur rotatif ou analogue et ses diverses applications
US3389746A (en) * 1967-06-21 1968-06-25 Avco Corp Rotary regenerator having concentric cylindrical matrices

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US12416263B2 (en) 2023-05-01 2025-09-16 General Electric Company Rotatable heat exchanger for a gas turbine engine

Also Published As

Publication number Publication date
DE2852561C2 (enExample) 1989-06-15
FR2413552A1 (fr) 1979-07-27
GB2009908A (en) 1979-06-20
FR2413552B1 (enExample) 1982-10-15
DE2852561A1 (de) 1979-06-07
GB2009908B (en) 1982-10-13

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